Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions

doi:10.1016/j.actaastro.2023.04.020

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions
	Ao Y(敖彧); Wu K(吴坤); Lu, Hongbo ; Ji, Feng ; Fan XJ(范学军)
刊名	ACTA ASTRONAUTICA
	2023-06
卷号	208 页码:281-295
关键词	Hypervelocity combustion Thermal nonequilibrium Two-temperature model Numerical simulation
ISSN号	0094-5765
DOI	10.1016/j.actaastro.2023.04.020
英文摘要	To characterize the impact of thermal nonequilibrium conditions in shock-induced combustion in high Mach number scramjet engines, a comparative numerical investigation has been performed. The combustor configu-ration was based on the HyShot II scramjet while the total enthalpy is 3.3 MJ/kg which resembles Mach 8 flight condition. The improved delay detached eddy simulation with Park two-temperature approach in combination with the vibration-chemical coupling model was employed in the nonequilibrium simulations. It is shown that under thermal nonequilibrium inflow conditions, noticeable stratification in the thermal state exists in the circumferential direction both in the combustor section and exhaust nozzle. In the inner core where the fuel mixes with the mainstream, flow deceleration caused by the heat release leads to a sufficient transformation of energy between the vibrational and translational-rotational modes approaching the thermal equilibrium state. However, the tau v,mix is quite large in the supersonic mainstream, whereby the thermal nonequilibrium dominates. For the case with higher Tv in the inflow, the fuel jet's penetration height is lower while the local viscosity is higher which results in poor mixing between the fuel and air stream. Nevertheless, a 400 K increase in inflow Tv gives a higher effective temperature, which promotes the dissociation reactions, shortens the ignition distance and yields an 8% increase in the overall combustion efficiency. With better combustion performance, an addi-tional 6% deceleration in the supersonic mainstream and the energy exchange rate between vibrational and translational-rotational modes becomes almost four times faster at the combustor outlet, which promotes the restoration of the thermal equilibrium state. Furthermore, under higher inflow vibrational temperature, the shock-induced combustion in supersonic crossflow becomes less stable with noticeable fluctuations in combus-tion heat release and local static pressure.
分类号	二类/Q1
WOS研究方向	WOS:000984645700001
语种	英语
资助机构	National Key Project [GJXM92579] ; Strategic Priority Research Program of ChineseAcademy of Sciences [XDA17030100] ; High-level Innovation Research Institute Program of Guangdong Province [2020B0909010003]
其他责任者	Wu, K
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/92230]
专题	力学研究所_高温气体动力学国家重点实验室
作者单位	1.(Lu Hongbo, Ji Feng) China Acad Aerosp Aerodynam Beijing 100074 Peoples R China 2.(Ao Yu, Fan Xuejun) Univ Chinese Acad Sci Sch Engn Sci Beijing 100049 Peoples R China 3.(Ao Yu, Wu Kun, Fan Xuejun) Chinese Acad Sci Inst Mech State Key Lab High Temp Gas Dynam Beijing 100190 Peoples R China
推荐引用方式 GB/T 7714	Ao Y,Wu K,Lu, Hongbo,et al. Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions[J]. ACTA ASTRONAUTICA,2023,208:281-295.
APA	敖彧,吴坤,Lu, Hongbo,Ji, Feng,&范学军.(2023).Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions.ACTA ASTRONAUTICA,208,281-295.
MLA	敖彧,et al."Combustion dynamics of high Mach number scramjet under different inflow thermal nonequilibrium conditions".ACTA ASTRONAUTICA 208(2023):281-295.